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NACA M3 AIRFOIL (m3-il)

NACA M3 AIRFOIL - NACA/Munk M-3 airfoil


Airfoil m3-il
Details Dat file Parser  
(m3-il) NACA M3 AIRFOIL
NACA/Munk M-3 airfoil
Max thickness 11.9% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M3 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0186000
 0.0250000 0.0251000
 0.0500000 0.0339000
 0.0750000 0.0400000
 0.1000000 0.0447000
 0.1500000 0.0514000
 0.2000000 0.0557000
 0.3000000 0.0595000
 0.4000000 0.0589000
 0.5000000 0.0550000
 0.6000000 0.0485000
 0.7000000 0.0396000
 0.8000000 0.0288000
 0.9000000 0.0162000
 0.9500000 0.0093000
 1.0000000 0.0020000

 0.0000000 0.0000000
 0.0125000 -.0186000
 0.0250000 -.0251000
 0.0500000 -.0339000
 0.0750000 -.0400000
 0.1000000 -.0447000
 0.1500000 -.0514000
 0.2000000 -.0557000
 0.3000000 -.0595000
 0.4000000 -.0589000
 0.5000000 -.0550000
 0.6000000 -.0485000
 0.7000000 -.0396000
 0.8000000 -.0288000
 0.9000000 -.0162000
 0.9500000 -.0093000
 1.0000000 -.0020000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M3 AIRFOIL (m3-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m3-il50,000927.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m3-il50,000526.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m3-il100,000937.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m3-il100,000534.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   m3-il200,000945.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m3-il200,000542.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m3-il500,000954.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m3-il500,000556.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m3-il1,000,000966.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m3-il1,000,000569.5 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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